WO2003080438A1

WO2003080438A1 - Aircraft ejection device for passengers and cargo

Info

Publication number: WO2003080438A1
Application number: PCT/ES2003/000125
Authority: WO
Inventors: Ricardo Manzano Goicoechea
Original assignee: Ricardo Manzano Goicoechea
Priority date: 2002-03-22
Filing date: 2003-03-17
Publication date: 2003-10-02
Also published as: AU2003215686A1; ES1052230Y; ES1052230U

Abstract

The invention relates to an aircraft ejection device for passengers and cargo. The inventive device is characterised in that it consists of a series of platforms (29, 30, 31) which are disposed in the form of correlative sections along the length of the aircraft, said platforms comprising a main frame (1). Rocket boosters (2) and a damping canvas or inflatable raft (3) are disposed under said main frame. Moreover, the aforementioned main frame (1) contains fuel housings (5) for the rocket boosters (2), housings for the booster (2) control systems, containers of inert gas for inflating the raft and cubicles (8) for emergency, position-finding equipment, etc., all of which are accessible by means of flap doors. The passenger seats (25) or the cargo are housed in a casing (11) of said main frame. The above-mentioned platforms (29, 30, 31) comprise an upper, lateral reinforcing structure (26) bearing parachutes (27) which is laterally installed in the fuselage (28) using ejection guides (33).

Description

"EJECTION DEVICE FOR PASSENGERS AND LOADS IN AIRCRAFT"

OBJECT OF THE INVENTION

The present invention, as expressed in the description of the Descriptive Report refers to an ejection device for passengers and cargoes in aircraft, which has been conceived and carried out in order to obtain numerous and notable advantages over other means existing in the passenger and cargo transportation in aircraft. To be used in cases of emergencies to protect them from direct impacts of the device either on land or at sea. The device is planned both to protect the passage, at the launch of the fuselage platforms of the aircraft and at its subsequent landing or landing.

The system is based on the rigidity of the platform for the protection to the content in the expulsion, in the coupling of a parachute system more to a pneumatic canvas system that will cushion the impact on the landing surface.

BACKGROUND OF THE INVENTION Other ejection devices are known, but independently in military fighters, where the pilot and co-pilot are self-ejected individually, known as the ejection system, arranged in the seats of these aircraft, and has the drawback of which is for a single person and would be unfeasible in aircraft destined for passenger or cargo transportation due to the instability that this would entail and the danger to the tickets of that aircraft since being launched independently would risk being burned by the propellants of the previous or later seats as well as the lateral ones, with the added inconvenience of the great space that they would occupy inside the aircraft. We also know the pneumatic raft inflation device or quick-fill tarpaulins intended for other uses independently. So. such as parachutes, location systems, survival, and more systems for rescue, but not all linked together, on a platform and synchronized as in this device here represented in this memory. Providing security known in the market today to any added circumstance.

DESCRIPTION OF THE INVENTION

Ejection device of platforms coupled to the chassis of the aircraft, by correlative sections, in the longitudinal direction of the aircraft, these sections may contain passengers or cargo interchangeably.

Said ejection is carried out by means of the coupling of propellant rockets in the lower part of the platforms, said propulsion acting temporarily, the expulsion of the platform is carried out longitudinally from stern to the bow of the aircraft, in order to avoid collisions between sections. Once released from the chassis.

The actuation time of the thrusters and the ignition duration will be calculated in order to avoid possible impacts with the airplane or parts detached from it, such as the upper part of the fuselage of the aircraft obviously detached previously.

The platforms will be equipped in its lower part with tarpaulins inflated with inert gas, in order to act as a pneumatic cone in case of direct impact on land or as a life raft in case of landing, trying to avoid possible personal or material damage to the contents in Jo on the indicated platforms.

Both the material used in the tarpaulins as well as the inflation pressures of the same must be calculated to avoid bounces on the ground and can cause the platform to overturn, and with a geometric configuration of the canvas that prevents the platform from tipping in the sea. and the subsequent sinking of the upper part of it where it is placed in the cargo or the passage.

The platform will be equipped inside with survival material, location, etc., indicated for emergencies.

In the event that the platform is intended for passage, passenger seats will be modified in such a way that they allow increased safety on the one hand, protecting head and upper extremities, and on the other a turning system that allows the adoption of the seat at an angle of frontal inclination towards the ground inferior to 90 ° that it presents in its normal state, in order to protect the passage in the most dangerous maneuver that is the one of ejection in full flight.

The passenger's fastening system to the seat will also be modified using safety belts with four tie-down points, with a simple connection and quick disengagement if necessary.

The platforms will be reinforced laterally by a structure composed of profiles that will give it mechanical consistency at the time of ejection, and to which the parachutes to be used will be attached.

Two parachutes will be used for each of the platforms to be launched, their attachment points will be located at the top of the structure that serves as reinforcement to the platform, so they are also designed to support the tensile loads that originate during the descent of it.

The propulsion system is located at the bottom of the platforms using four propellers per one of them. These will be located in each of the four vertices of the rectangle that forms the platform.

Its ignition must be simultaneous and of equal power to make an adequate launch.

Before launching, the seats will have taken the inclined position indicated above.

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 shows a bottom view of the platform where the ejection devices and damping canvas and their interiors are located. Figure 2 shows a top plan view of the platform showing its interior distribution of all the rooms for its operation and storage of elements.

Figure 3 shows a top plane perspective of the deck or floor where seats, or hatch loads will be fixed for access to rescue equipment. Figure 4 shows a plane of a seat seen from the front where you can see the different fixations and renovations for the complete safety of the passengers.

Figure 5 shows a lateral plane of the seat where the fixations to the platform and its mechanisms can be observed, as well as the anatomical design of the same.

Figure 6 shows a side perspective of the whole assembly showing the position of the seats and protections of the structure.

Figure 7 shows a perspective view of the entire assembly within the fuselage of the aircraft seen from above.

Figure 8 shows a perspective plan of several platforms located inside the fuselage of the plane seen from above.

Figure 9 shows a cross-section of the entire assembly, where we see both the platforms and the fuselage and other elements that make up the central part of the aircraft being able to observe the ejection guides.

Figure 10 shows a cross-section of the entire assembly where the separation of the upper fuselage and subsequently the platform is observed, leaving it free of the lower fuselage. Figure 11 shows a view of the aircraft or fuselage where the ejection sequence of the upper fuselage and the platforms can be observed successively and the order of launch.

Figure 12 shows a side view of the entire platform assembly with all braking and emergency systems in operation.

DESCRIPTION OF A PREFERRED EMBODIMENT

As the system has been described, it is basically composed of two structural mechanical elements, the inner platform (1) and the reinforcement structure (26).

In these elements the necessary devices for the ejection of the platform (2) will be installed, reduce the descent speed by means of the parachute system (27), and dampen the landing or landing impact by inflating the damping tarps (3 ). The platform will be constructed with profiles and plates of reduced weight and high resistance to facilitate the installation inside of all the devices and elements necessary for its correct operation (1). The inner part of this platform as described above will consist of static parts such as pressurized fuel (5) and inert gas (7) tanks, survival elements, etc., and on the other hand dynamic elements such as which, in the movement of the seats at the time of the launch and cushioning canvas the moment of its inflation (3).

It must also complement the access to the oxygen distribution system that must be available for the passage at the initial moments of the launch and until it reaches an established height at which breathing is natural. Well installed on the platform (1) or inside the seats or fixed to them (25).

In figure 1 we can see the distribution of the ejection systems that will ensure the correct expulsion of the platform (1) and the fuselage of the apparatus (28).

We can also observe in the central part of the platform the exit of the damping canvas system (3) with the two functions described above to avoid the direct impact on the platform at its landing and, that of the flotation system in the case of landing ,

In figure 1 we see the distribution of seats (25), fuel tanks (5), inflation tanks of the damping canvas (7), etc.

Access to the interior of the platform will be through the hatches (12) arranged as indicated in Figure 3, with access to the cabin (10) for all rescue equipment.

The construction of the seats (25) although it varies with respect to those normally used does not represent the novel part of the invention, being able to observe on the other hand the superior protection previously described, in figure 4 position (14), the anchorage devices to the seat position (16), and tilting system of the seat towards the front for protection of the passenger position (21).

The upper structure (26) will be designed in such a way that it provides sufficient rigidity for the moment of expulsion preventing the platform from deforming due to inertial forces, wind pressure due to the speed of the aircraft, on the other hand it must give sufficient protection to the passage or load, and must be able as can be seen in figures 11 and 12 to withstand the action of the parachutes the moment of their opening, which will be a very important load when the deceleration of the platform , said effort must be distributed between the structure of the platform in order to avoid deformations that could damage the assembly. We must highlight the modification to be made in the fuselages

(28) so that the system can be effective, modifying the fuselage of the aircraft to be able to eliminate the upper part of the structure of the aircraft, thus allowing the exit of the platform at the moment when the drive rockets are activated (2 ), as we can see in Figures 9, 10 and 11, as indicated in Figure 1, it has in its lower part a main chassis (1), propellant rockets (2) housed in their corresponding cubicles isolated from the rest of the platform and its components by a passenger compartment (4), in the central part of the base, the damping canvas or raft will be available as indicated (3).

In figure 2 an internal section of the platform can be seen in which there is a part for the fuel housing (5) of the propellant rockets, and for the control systems thereof (6), the pressure tanks of Inert gas for inflation of the raft or damping canvas (7), the location and communication equipment, GPS, stations, etc. will be installed in the cubicle (8), the passenger compartment (9) being the place destined for the batteries of power to the systems of control of the motors, of location and communication. Each passenger will have their personal emergency and survival equipment that will be accommodated in the cubicle (10). In figure 3, a plan view of the upper part of the platform is arranged, n which is observed (12) as the hatches that give access to the interior of the platform chassis, the rest (1) being what it will constitute the floor where the passage or the cargo object of the transport will be housed. In figure 4, the necessary characteristics to be implanted in the passenger seats are detailed, so that during the expulsion, their situation can be considered safe, these being reinforced inside with light and resistant material, with greater incidence in the backrests ( 13). As stated above, the upper part of the seat is covered by an upper visor that will protect the head and upper extremities during expulsion (14), given the expected violence of the forces that will act on the passenger, at the time of the expulsion, a system of subjection of the same to the seat will be designed that ensures the total union of the passenger-seat assembly in order to avoid injuries in the joints, therefore the sides of the seat will be enveloping (15), will have the fastening system (16) of reinforced safety belts, the hitching of the same will be fast, with the possibility of an urgent untapping (17), as a complement to these systems there is armrest (18), folding footrest (20) ) and straps that secure the seat legs (19). There is also a rigid system for joining the seat to the platform (21) that will allow it to tip over a certain angle forward for passenger protection. Figure 5 is a side view of the seat in which is detailed (22) which is the rear passenger protection canvas, in the prevention of possible blows against the mechanisms of the front seat swingarms. As indicated (20) it is an extendable footrest operated by the mechanism (23), (24) the hydraulic system governing the tilting being the seat described above.

Figure 6 is a side view of the assembly of a complete platform where the direction of the seats (25) can be contemplated, all aligned in the direction of advance of the aircraft except the first, that is, the one located in the bow of the platform, which found rotated 180 ° with respect to others, for better passenger protection. The structure (26) is responsible for giving mechanical consistency to the assembly as well as housing in its upper part (27) the parachutes that will be activated at the time of starting the descent. Figure 7 shows a plan view of the elements indicated above and their placement with respect to the fuselage of the aircraft (28). Figure 8 shows a view of all the various platforms (29), (30) and (31), which will be mounted on the fuselage of the aircraft (28) and will be completed along the fuselage, the entire passage of the aircraft. It is to these platforms that an exit order must be given at the time of ejection, so it will be done consecutively from bow to stern, with the determined rate.

Figure 9, details a cross section of the fuselage of the aircraft in which we observe the arrangement of both the platforms, the fuselage and other elements that make up the central part of the aircraft, highlighting the entire set (33) that are guides of expulsion of the platforms and the (32) that is the parachute fixed to the top of the fuselage for later recovery of the same. In figure 10 we can see a sequence of action of the complete system in which the upper part of the fuselage is first ejected and then the platform object of this study.

Figure 11 shows the sequence of expulsion of the platforms (34), in relation to the fuselage, clearly indicating that the first ones to be expelled are those located aft of the aircraft continuing consecutively until reaching the one located in the bow, later the expulsion will produce - the deployment of the parachutes (27), of which the platform (1) is suspended, by means of stabilizing cables (35) and they significantly slow down the descent of the same proceeding before impact, whether on land or at sea, inflation of the raft or damping canvas (3).

Claims

R E I V I N D I C A C I O N E S

1 ^a . Ejection device for passengers and cargoes in aircraft, characterized in that it consists of a series of platforms (29, 30, 31) that are coupled to the floor of an aircraft in which the upper part of the fuselage (28) can be separated when desired, the platforms (29, 30, 31) are arranged by correlative sections throughout the aircraft, can carry passenger or cargo seats (25) and have a main chassis (1) under which are isolated propellant rockets (2) in a passenger compartment (4) and an inflatable raft or damping canvas (3); inside the main chassis (1) there are some fuel housings (5) for the propellant rockets (2) there are also housings for control systems of the propellant rockets (2), inert gas tanks for swelling of the raft or damping canvas (3), cubicles (8) for location, signaling, GPS and radio stations equipment, cabinets (9) for power batteries for the location, communication and control systems of propellant rockets (2), and cubicles for emergency and survival material (10) of passengers; the interior of this main chassis (1) is accessible by existing hatches (12) in a cover (11) thereof on which the passenger seats (25) or cargo are located; the passenger seats (25) have a reinforced backrest (13), protective visor (14), wraparound sides (15), reinforced safety belts (16) that have an emergency unlocking device (17), armrest (18) , folding footrest (20), leg support straps (19), tilting foot (21) connecting the seat (25) to the main chassis (1), protective canvas (22) covering the tilting foot (21), extensor mechanism (23) of the footrest (20), hydraulic system (24) that drives the tilting foot (21); The platforms (29, 30, 31) have a lateral and upper reinforcing structure (26) that carries a parachute (27) and is installed laterally in the fuselage (28) by means of ejection guides (33) of this fuselage (28). ); the fuselage (28) has its own parachute (32); the platforms (29, 30, 31) are suspended from their parachutes (27) by means of stabilizer cables (35); in the platforms (29, 30, 31) all seats (25) look in the direction of advance of the aircraft, except the first or bow, which is rotated 180 °.